高亚声速层流飞机是现阶段飞机设计的一个重点研究方向，可以有效提高飞机气动性能，增加航程航时等关键指标，但层流翼型在低速条件下与传统翼型相比气动特性较差。利用改进的剪切层自适应IDDES方法针对某特殊设计的层流验证机层流翼段进行分析及改进，抑制其由于翼型本身及翼身结合处的三维效应在大攻角状态下所引起的流动分离，使得翼段在低速大迎角状态下获得相对较好的气动特性。结果表明通过对层流翼段的翼型前缘修型，可以在低速条件下显著抑制流动分离，使得层流翼段在低速性能提升的同时在高速条件下也能保证较好的气动特性。
High subsonic laminar aircraft design is a key research direction of aircraft. Laminar airfoils play an important role in improving key indicators such as aerodynamic performance, flight range, and flight time. However, their aerodynamic characteristics are worse than those of traditional airfoils at high angles of attack and low speed. A shear layer adaptive improved delay detached eddy simulation method is used to analyze and improve the laminar airfoil of the laminar verifying aircraft. The flow separation at the leading area caused by the three-dimensional effect of the airfoil itself and the wing/body junction at high angles of attack are suppressed and keep good aerodynamic characteristics at a low Mach and high angle of attack by the modified laminar airfoil. The results show that by modifying the leading edge of the laminar flow airfoil, the flow separation can be significantly suppressed at low speed, thus significantly improving the aerodynamic characteristics of the laminar flow airfoil while keeping good aerodynamic characteristics at high Mach number.
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